Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Systems and methods are provided for providing stability support. The system may include a movable foundation that moves on a surface, and a base rotatably mounted to the movable foundation. A leveling platform may be adjustably mounted to the base and can pivot around a pivoting axis intersecting the base. A control arm connects the leveling platform and the base, and can effect the pivoting of the leveling platform by adjusting the length of the control arm. An alternative system may include a supporting scaffold that is adjustably connected to a movable foundation by at least three control arms. The at least three control arms can change length such that an angle of the supporting scaffold from the movable foundation changes.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of landing gears that are extendable from and movable relative to the central body. The plurality of landing gears are configured to transform between a flight configuration and a surface configuration. In the flight configuration, the landing gears are extending laterally away from the central body and not in contact with a surface below the central body. In the surface configuration, the landing gears are extending towards the surface below the central body. When the landing gears are in the surface configuration, the landing gears are configured to support a weight of the central body on the surface and transport the UAV over the surface by moving one or more of the landing gears relative to the surface.

An unmanned aerial vehicle (UAV) landing method includes detecting, via one or more sensors on-board the UAV, a positional change of the UAV while the UAV is airborne; and generating, with aid of one or more processors on-board the UAV and in response to the detected positional change, one or more command signals to decelerate one or more rotor blades of the UAV, thereby causing the UAV to land autonomously.

An undercarriage for an aircraft, an aircraft and an aircraft landing method are disclosed. The undercarriage includes: at least three bendable mechanical arms, wherein each mechanical arm includes a mount, a first link and a second link located in a same plane, the mount is connected with the aircraft, the mount is rotatable about an axis perpendicular to a bottom surface of the aircraft, the other end of the first link is pivotably connected with one end of the second link, and the other end of the second link is connected with a rotating wheel; a force feedback device configured to detect whether or not the mechanical arms receive forces, respectively; and drive mechanisms configured to respectively drive the mechanical arms to move such that in an outspreading process of the undercarriage, the drive mechanisms drive any one of the mechanism arms to be maintained in a current state when the force feedback device detects that the one of the mechanism arms receives a force.

Methods and apparatus are provided for launching and landing unmanned aerial vehicles (UAVs) including multi-rotor aircrafts. The methods and apparatus disclosed herein utilize positional change of the UAV, visual signal, or other means to effect the launch or landing. The methods and apparatus disclosed herein are user friendly, particularly to amateur UAV users lacking practice of operating a UAV.

An undercarriage for an aircraft, an aircraft and an aircraft landing method are disclosed. The undercarriage includes: at least three bendable mechanical arms, wherein each mechanical arm includes a mount, a first link and a second link located in a same plane, the mount is connected with the aircraft, the mount is rotatable about an axis perpendicular to a bottom surface of the aircraft, the other end of the first link is pivotably connected with one end of the second link, and the other end of the second link is connected with a rotating wheel; a force feedback device configured to detect whether or not the mechanical arms receive forces, respectively; and drive mechanisms configured to respectively drive the mechanical arms to move such that in an outspreading process of the undercarriage, the drive mechanisms drive any one of the mechanism arms to be maintained in a current state when the force feedback device detects that the one of the mechanism arms receives a force.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot.

An unmanned aerial vehicle (UAV) and a landing method thereof are provided. The landing method includes the following steps. Firstly, a depth image of a scene is obtained. Next, a landing position is determined in accordance with the depth image. Next, a height information of the landing position is obtained. Next, a plurality of relative distances of the landing gears relative to the landing position are adjusted in accordance with the height information to make the relative distances substantially the same. Then, the UAV lands on the landing position.